Tail-skid for aeroplanes.



H. KLECKLEH, TAIL SKID FOR AERGPLANES. APPLICATION FILED APR.1'.191r.

u Patented Jan.V .7, `1919.

` HENRY KLECKLaEV.

4 which the two'remaining sides are movable.

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HENRY xLncnrnn., or terrano, New venir, Assis-Non 'ro cun'riss ennorLaNn AND i Moron CORPORATION, a conronarroiv Or New iront. y

rarnfsmn non annortanns.

To all whom 'it may concern:

Be it known that l, HENRY KLEOKLER, a citizen oi the United States, residingat Buffalo, in the county of Erie and State of New York, have invented certain new and useful Improvements in Tail-Skids for Aeroplanes, of which the following is `a speci cation. i

My invention relates to tail skids for aeroplanes This invention is characterized especially by compactness, simplicity of construction, and increased strength. ln-

stead of the usual attenuated elastics, elas ticsy of Vdecreased len'tharel used. These elastics embrace the forward upper end of the skid bar and are secured or fastened to an improved triangulated support. One of the sides of this support extends substan-- tially vertically and is fixed with respect to the aeroplane body togserve as an vaxis about Said remainingsides are integrally united and equipped with downturned ears between' which 'the skid bar is lulcrum'ed. By

such an arrangement movement of the skid bar in both avertical and a horizontal plane is obtained anda two point distribution ci" the landing impact provided. Moreover,

' the support and the steering partel are inthe movable part ofthe said Vsupport may or may not be` coupled u with the lateral directional control `sur ace 'or surfaces for steering purposes. In any Yevent the elastica,

closed completely within the fuselage or body. y if 0f the drawings,` wherein likecharacters 4of reference designate like or corresponding' parts z Figure 1\1s a longitudinal sectional view of the tail end of an :aeroplane fuselage illustrating thel tail skidV and its support ormounting -in side elevation;

` will impart te the sld bar corrresponding V"Fig". 2 is a section' on the'line 2--2 of 1, and Y 1' f Fig. 3 is a' perspective view of the movlable portion ofthe skid support.

t In they embodiment of the Ainvention selected for illustration, the slrid bar v1 0 is shown as of the steering typein that appropriate 2 connections have been AprpvidedV :'whereby movement ofthe rudder orgiateral directional control. surfaces (not shown) specification or tenere raient movements `Contriil leads 11 to be connected Ears 13 integrally united with the movable part o the triangulated support serve as the skid bar fastening means. These ears are brazed orwelded on the support at apoint adjacent its lower extremity and at a' point removed trom the shock absorber'elastics 14. The elastics (see Fig. 1) embrace ratenteu aan. v, rara. app11canonmeaaprn16,1917. seriainaieatst. 5

es the. movable-part of the triangulated sup lportA and the skid bar 10. h/loreover, the

elastics are quite short and inf tact normally i malntain the `upper end of the skid bar in Acontiguous Contact with the lower forward edge of the triangulated support.` In this connection it will be noted also that the skid bar s`-prov`ided at itsY inner upper end with f l an enlargement 15,and the triangulated sup-f-VVV port with an abutment 16, whereby casual displacement of the elasticsflft` is prevented. The triangular support," designated as an entirety by the numeral 17, comprises a 1 movablepart 18 andaxed part19. Said xed part 19 extends substantially vertically from a `point in y"the plane of the upper longe'rons 2Q of the fuselage to a oint in the laiie of the lower longerons 21. orizontal 'uselage struts 22 interconnecting said lonerons 20 and 21 support said fixed part 19.

he Apart 18 is movable about the xed part 19as an axis and is so mounted with respect to said iixed part that its 'extremities engage said parts atipointsfwidely spaced and preferably in thegvicinity ofthe iXedpart extremities.' The fixed part 19 is in:` the l.nature of V arranged or diverging metal rods and the movable part 18 is constructed of metal` tubingV terminally flattened and bent intermediate its ends to constitute two sides ofthe support 17 Ywhen considered in its entirety. A wide distribution of the landinggshocks or impact is obtained by this arrangement. ln other words2 the impact is f distributed to points in the immediate vi` cinity of the cross struts 22 which are eRectually'braced by the rods 19.

A tiller 23 of substantiallyV-forinina.

horizontal plane is brazed te themovable part 18 of the triangulatedsupport. Its location is preferably at a point in the vicine ion ict

-ity of the lower extremity of the triangle with the arms of the tille'r extending rearwardly and laterally for termination at points in the plane of the vertical axis of the tail skid as defined by the fixed part 19.

Shackles 24 are utilized for fastening the control leads 11 to said tiller extremities. The arms of the tiller extend rearwardly for increased leverage in manupulating the tail skid for steering purposes. Furthermore,

the triangulated support, in its entirety,

(hence the tiller 23) is inclosed in the body of the craft.

The rear outer end of the skid bar 10 is enlarged -as at 25 and equipped with a wearing plate 2G of appropriate form. Said enlargement 25 provides for increased strength and the plate 26 for increased longevity of the skid. In addition, appropriate means such as the laminated or veneered strips 27 may-be provided interiorly of thefuselage to prevent puncture of the fabric covering should the tail'skid be laterally deflected to an unusual extent.

While in the foregoing there has been illustrated in the drawings and described' in the specification such combination and A when made in claims.

arrangement of elements as constitute the 'preferred constructionor embodiment of body of the aeroplane.

3.' A tail skid Afor aeroplanes according to claim 1 characterized bythe fact that the skid bar is movable with and with respect to the support.

4. A tail 'skid for aeroplaiics according to claim 1 characterized by the fact that the support, including its axis, is of substantially triangulated form.

l 5. A tail skid for aeroplanes including an inclined support, a skid bar yiedingly connected with' the support and inclined in the same general direction and a pivotal connectionbetween the skid bar and support.

6. A tail skid for aeroplanes according to claim 5 characterized by the fact that the support is movable laterally with the skid bar in response to' laterally directed shocks.

7. A tail skid for aeroplanes according to claim 5 characterized by the fact that the support for the major part is inclosed in the body of the aeroplane.

8. A tail skid for aeroplanes including a laterally movable support, a skid bar of a construction such thatit extends substantially parallel with the support throughout a portion of its length, and spaced connections between said bar and'said sup ort comprising elastic means and the pivot means respectively. l

`9. A tail skid for aeroplanes comprising -a. pivoted laterally movable support, the major portion of said support lying at one side of its pivot axis, a skid bar, and a connection between said bar and said support.

l0. The combination with an aeroplane A including a fuselage, of a tail skid extended at one end intothe fuselage, a support inclosed in the fuselage and mounted to swing on a substantially vertical axis, and an elastic connection between the tail skid and the movable support, the type of connection be ing such that it is completely inclosed whether or not it is distended.

In testimony whereof I hereunto aiix my signature.

HENRY KLECKLER. 

